Missile retaining device



Jan. 27, 1959 F. HERRMANN 2,870,677

' MISSILE RETAINING DEVICE Filed Feb. 3, 1955 INVENTOR. Fre Herrmann @10finaa'rr mam-x5.

'riphery of the launching tube 1.

United States Patent MISSILE RETAINING DEVICE Fred Hermann, WestEnglewood, N. J., assignor to the United States of America asrepresented by the Secretary of the Army Application February 3, 1955,Serial No. 486,039 6 Claims. (Cl. 89-1.7)

This invention relates to a missile retaining device more specificallyto a device for retaining a missile such as a rocket in its firingposition in a launching tube.

It is a primary object of this invention to provide a missile retainingdevice of symmetrical design, compact and easily attached to a launchingtube.

A further object of the invention is to provide a retaining devicepossessing substantially the same durability and life as the launchingtube itself and having a high break loose yet requiring only a lowinitial force to load.

Another object of the invention is to provide a retaining devicecompletely automatic in operation.

A still further object is to provide a retaining device.

cheaply constructed and easy to service.

Other objects and advantages will become apparent during the course ofthe following description and upon examination of the accompanyingdrawing in which:

Figure l is a longitudinal sectional view of a retain-- ing deviceconstructed in accordance with the invention and applied to a launchingtube as shown in a plane identified by line 1-1 of Figure 2, a

Figure 2 is an end view of the missile launching tube illustrated inFigure l,

Figure 3 is an exploded perspective'view of the various components ofthe retaining device, and Figure 4 is a plan view of one retainingdevice taken in the plane 44 of Figure l and looking in thedirection ofthe arrows.

Referring now more particularly to the drawings, ref- I erence character1 denotes generally a launching tube provided with a series oflongitudinally disposed fins 2 integral with the inner periphery of thetube and extending radially inwardly towards its axis. 3 to a distancesuch that their free edges are separated a distance equal. to theoutside diameter of the bourrelet ring 4 of the boost; er portion of amissile 5. Legs 2 normally extend to the one end 8 being of concavecontour to fit the outer pe-;

riphery of the bourreletring 4 of missile and the opposite' end 9 beingof convex contour to fit the inner pe- The end 9 of the housing 7 isprovided with a pair of longitudinally aligned threaded taps 10 toreceive screws 11 whereby the house a ing is attached to the innerperiphery of the rearward edge of the tube to prevent rotation of thehousing and to securely fasten it to the tube 2. The housing 7 isprovided with a pair of longitudinally aligned wells 12 and 12a boredfrom the concave end 8 to a distance deep' enough to completely containa pair of locking plungers 13 and 13a. The plungers 13 and 13a areaxially bored at their upper ends as at 14 to provide a receptacle forcoil springs 15 and 15a which act, 'in an obvious manner, to urge theplungers radially inwardly of the tube 2. Means for retaining theplungers 13 and 13a in the respective wells areprovided by cap screw 16which is engaged in a threaded tap 17. As shown upon Figure 1 the headof screw 16 fits within a counterbore 18 extending axially with tap'17." Both mp 17 and counter- 2 I bore 18' are located centrally betweenwells 12 and 12a and the well 18 is of a diameter greater than theseparation of bores or wells 12 and 12a so that the head of screw 16when threaded into tap 17 overlaps bores 12 and 12a whereby the plungersare retained in their respective wells against the thrust of springs 15and 15a. For this purpose concave notches 19 are formed on the lowerpart of the inner sides of plungers 13 and 13a as best seen in Figure 3.When the plungers are intheir position in the respective wells and thecap screw -16is threaded into assembled position, the head of screw 16'will rest in milled out spaces 19, and, in a manner obvious frominspection of Figures 1, 3 and 4, the plungers are retained in theirrespective bores and also prevented from turning therein. Due to springs15 and 15a the plungers .are urged towards the bourrelet ring 4. Therelative radial dimensions of bores 12 and 12a and plungers 13 and 13aare such that the latter may be completely contained within the boresupon passage of the bourrelet ring 4 under them. As best viewed upon;Figures 1 and 3, the plungers 13 and 13a are provided with beveledsurfaces 21 and 22. The planes of bevels 21 make a smaller angle withthe axis of the respective plunger than the planes of bevels 22 thusmaking it easier to push the bourrelet ring 4 of missile 5 into positionbe tween the fingers 13 than to release it from such position. lodgementof the bourrelet ring 4 from between the plungers 13 and 13a when themissile 5 is in firing position.. Also, the plungers are provided withlongitudinal slots 23 and 23a (see Figures 1 and 3) so that when thecomponent parts of the retaining device 6 are in assembledrelation theseslots are coplanar with one an-.

other and also with notches 24 cut in housing 7 to therehousing 7 togases, suitable chamfers 25 have been cut on the edges of the housing.(See Figure 3.) I

W'hile only two retaining devices 6 have beenillus trated diametricallypositioned within tube 2, more can, v

be added if desired, in which event they will beequiangularly spacedabout the inner periphery of the tube, The tubes are preferable made ofstainless or-other-cor rosion resistant steel.

. In order to mount a retainer on a launching cap 'screw 16 is threadedinto place.

The operation of the device is completely automatic.

The missile 5 is inserted into the tube 1 in a rotational position whichwill let the fins 26 clear the retaining dcvices and fins 2 (see Figure2), and then the-missile isg pushed in the tube until the bourrelet ring4 snaps be-,

tween plungers 13 When the rocket is fired, the thrust down the tube.

It will be apparent from the foregoing thatI-have provided a simple, yetdependable retaining device which,

" is positive and'reliable in operation and extremely-easy to repair,service and replace; All plungers are duplicates and henceinterchangeable. Hence it is not neces-y sary to replace the entireassembly'as any. part .canfbe;. l a 1Y; P d.- .Ths snl g oo rsq ireqgiis"a screw driver.

Bevels 21 will therefore prevent accidental dis-- tube,- the fins 2 arecut away at their rearward ends over-a; length equal to the length of aretaining device tobe. mounted. .Screws 11 are then insertedthroughaholcs drilled in the tube and into taps 10. "The springs .15 andfingers 13 are then inserted into the wells 12 andthe It is to beunderstoodthat the form of the invention herewith shown and describedisto be taken as a preferred example of the same, and that various changesin the shape, size and arrangements of parts may be re-. sortedtofwithout' departing" from; the spirit of my invention; or the scope ofthe subjoined" claims;

1. a mechanism for releasably retaining a self-propelledmiss'ileinlaunching positi'onwithin a tube, a'hon ing adapted for" rigidsecurernent to the inner periphery ofsaid t'u'be, there being a pair ofbores radially dispnsed in spaced relation in said' housing with theiraxes in a common plane through the axis of the tube, said housing havinga notch in the wall between each said horeand the respective forward andrearward face there'- I of; a pair of plungers each fitting a respectivebore;

h said plunger having a slot in its inner end said slots "g disposed incoplanar relation with one another to a continuous passage with saidnotches in said housing longitudinal of said tube, a coil spring in eachbore urging'each plunger radially inwardly, and a cap sfe'rew' fixedwith said housing between said bores and engaging both said plungers toprevent rotation'fof said plungers and limiting radial inward movementthereof under'ur' e'of said coil springs. i

' 2'. In a device for releasably retaining a self-propelled missilehaving abourrelet ring fixed coaxially' about its rearwardend, alauncher tube of greater diameter than- I the bourrelet ring, a housingrigidly secured to the inner periphery of said tube at the breech endthereof, there being first and second boresin said housing disposedradially ofsaidtube with their axes in a common plane through the axisof said'tube, said housing having a notch;

in-- the wall between each said bore and the respective forward andrearward face thereof, a pair of plungers each 'slidably mounted in arespective bore, each. said plunger'having a slot} in its inner end',said slots being disposed in coplanar relation with one another to formV a eon'tinuouspassage with said notches in said housing longitudinal ofsaidtube, spring means carried by said housing and urging ea ch'plungerradially inwardly, and a cap screw fixed with said housing and engagingboth said plungers to prevent rotation and limit radial inrearward end'in radially spaced relation therewithya launcher tube of greaterdiameter than said ring, at least one'hou'sing rigidly fixed to theinner periphery of said tube at the breech end thereof, there being apair of spaced bores in said housing with their axes in a comrnon planethrough the axis of'said tube, said'housing having a notch in the wallbetween each said bore and the respective forward and rearward facethereof, a pair of plungers each slidably' fitting a respective bore,each said plunger having a slot, in its inner end, said slots beingdisposed in coplanar relation with one another to forina continuouspassage with said notches in said housing longitudinal of said tube, aspring in each bore urging its plunger radially inwardly, and a singlescrew threaded into said housing between said bores and havmg a headoverlapping said bores, said head fitting recesses in said plungerswhereby said plungers are prevented fromrotation and limited in outwardmovement, said ring releasably fitting between said plungers when themissile is in firing position in said tube.

[4. In a missile retaining devicefor indexing a missile infiringposition in a launching tube comprising, a housnig'jrig'idIy'securedto the inner wall of said tube, a pair oispring-biased indexingplungers slidably mounted with- .in apair of spaced bores in saidhousing disposed radially' to the longitudinal axis of the launchingtube, said housing and said plungers having aligned slots along .wardmovement thereof, said ring releasably fitting be-, tween said plungerswhen the missile is in launching potheir inner faces to form acontinuous passage longitudinal of'said tube, and'a ca'p screw fixedwith said housing and disposed medially between said bores and retainingsaid plungers in said bores 'and limiting their radial travel therein,said'plungeis' being completely contained in said bores; when biasedoutwardly by the pass-.

the radial direction no t greater than the corresponding; dimension ofsaidfins, there being a pair ofaxially spaced hor es in each housinghaving their axes radial to the axis of said tube each? said housinghaving a groove in the wall between the respectit'e forward andrearward" face thereof, a pair of plunger-s each slidably fitting arespective bore each said plunger having a groove in its inner end andbeing disposed in coplanar relation with: each other to form acontinuous passage with'said grooves in said housing longitudinal ofsaid tube, a cap screw threaded into said housing between said bores andhaving its head overlapping each bore, said plungers being.

cut away at their" radiallyinward ends to accommodate thehead' of saidscrew, whereby said plungers are prevented from rotation in" said boresandlimited to translation frorn'a first position entirelyhoused withinsaid b'o'res, to a second position projecting a short distance onlytherefrom, f

' 6. The combination with a rocket launcher tube hav-; ing a pluralityof equiangularly-spaced, longitudinally and radially-inwardlyextendingguidefins whose longitudinal inward edges define a circle ofsubstantially the same diameter as" a ioclifetT'toj be launchedtherefrom, at least twoof apair of diametrically opposed fins being'cutaway at their. rearward ends to accommodate a pair of substantiallyrectangularhousings having avconeave inner face rigidly secured'totheiinnef peripheryof said launching tube, each said housing havingapair of spaced-bores disposed radially of said tubethere being a groovein its inner face communicating between each said bore, and therespective forward and-rearward end of aid] housing, a plunger in" eachsaid bore said'plunger having, a groove in its inner end disposed inlongitudinal align; menfwith the corresponding. "groove in the adjacent.plunger, said grooves ijn.saidho usingforming continuous I passageparallel with thea-xis of'said tube, a coil qspring in each said" here,normally urgingsaid plungers in:

wardly, said plbng'ersbeing-beveled on their outer ends, in twoangularlyrelated planes, said planes intersecting in a lineperpendicular to means of said tube, the confronting bevelso saidplungers beingv at alesser angleto lilngers, than the second bevels, andre- 2,460,929 Gofi 'Feb. 8, 194g,

701,984 Teree Feb. 15 1955",

2,712,270 Green- July 5, 19-55 a FOREIGN-PATENTS 1 9 14341 France June-17, 19 14 fsl f o limiting movement of saidi'plungersin

